Turbine blade platform with impingement cooling
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United States of America Patent
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Jan 7, 2014
Grant Date -
N/A
app pub date -
Apr 21, 2011
filing date -
Apr 21, 2011
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Abstract
A turbine rotor disk with rotor blades secured within slots, where the rotor disk includes a radial extension that occupies a space where a dead rim cavity would be formed, and in which the radial extension includes a cooling air chamber with impingement cooling air holes directed to discharge impingement cooling air to a backside surface of the platforms of the blades.
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